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Turbojet architecture with two fans at the front

a technology of turbines and turbine blades, which is applied in the direction of liquid fuel engines, machines/engines, combustion air/fuel air treatment, etc., can solve the problems of reducing efficiency and increasing the weight of engines

Active Publication Date: 2008-08-19
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The invention is a turbojet with two fans that solves the problem of overhanging. The rear fan's blades extend into the by-pass air flow from a wheel connected to its drive shaft, and the front fan's blades are supported by an outer stator in the by-pass air flow. The front fan and rear fan are counter-rotatable fans. The design also includes additional bearings between the drive shaft and the front fan, and between the drive shaft and the rear fan. The thrust bearing of the front fan is supported by the second intermediate casing, and the inter-shaft bearing is a roller bearing or a thrust bearing. The first intermediate casing supports the rotary shaft of the rear fan via an axial thrust bearing, and the drive shaft of the front fan via an inter-shaft bearing. The design also includes a roller bearing interposed between the second intermediate casing and the drive shaft of the rear fan. Overall, the invention solves the problem of overhanging and ensures efficient airflow.

Problems solved by technology

Nevertheless, gearing increases the weight of the engine considerably and also reduces efficiency.

Method used

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  • Turbojet architecture with two fans at the front
  • Turbojet architecture with two fans at the front
  • Turbojet architecture with two fans at the front

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Effect test

first embodiment

[0023]In a first embodiment, shown in FIG. 1, the inter-shaft bearing 80 is a roller bearing and the bearing 81 is a thrust bearing. In this version, the axial forces of the front fan 3 that are supported by the second intermediate casing 60 cross the fan casing 12 before being taken up by the thrust take-up bars 33 in the intermediate casing 2. From a mechanical point of view, this technique is simple, but in terms of transferring forces, it is complicated.

second embodiment

[0024]In a second embodiment, shown in FIG. 2, the inter-shaft bearing 80 is a thrust bearing and the bearing 81 is a roller bearing. In this version the intermediate shaft 6 supports the axial forces of the front fan 3 and transfers these forces directly to the downstream intermediate casing 2 where they are taken up by the thrust take-up bars 33 in the intermediate casing 2. In terms of transferring forces, this technique is simple, but in terms of the connection between the thrust bearing 80 of the front fan 3 and the drive shaft 6 of the rear fan 5, it is complicated.

[0025]Both fans 3 and 5 can turn in the same direction. Very advantageously, however, the two fans 3 and 5 are counter-rotatable and driven by a working turbine having an inner rotor and an outer rotor, said two rotors having rings of rotor blades in axial alternation. This disposition reduces both the length and the weight of the working turbine because of the absence of a stator.

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Abstract

A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.

Description

[0001]The invention relates to a three-spool by-pass turbojet with a high by-pass ratio, the turbojet having a front fan and a rear fan at the front of an intermediate casing that presents an outer structural grid in the by-pass air flow and an inner structural grid in the main air flow, the fans having blades that extend radially outwards to a fan casing, which fan casing outwardly defines the by-pass air flow, the turbojet also having a low-pressure compressor for compressing air coming into the channel for the main air flow, said front fan and said rear fan being rotated directly, and separately, by two shafts that are coaxial.BACKGROUND OF THE INVENTION[0002]In a modern, high-power turbojet with a high by-pass ratio, the fan has a large diameter, and the peripheral speed at the tips of the blades is proportional both to this diameter and to the speed of rotation of the fan. In order to obtain good efficiency, the peripheral speed must be lower than the speed of sound. In a conve...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): F02K3/065F02K3/072F02C7/04F01D25/16F02C7/06F02K3/04F02K3/06F04D29/04F04D29/056F04D29/059F04D29/32
CPCF01D25/162F02C7/06F02K3/04F04D29/0563F04D29/059F04D29/321F02K3/065Y02T50/671Y02T50/60
Inventor BART, JACQUESBEUTIN, BRUNOLEBRET, YANN
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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